EPPLER 856 AIRFOIL (e856-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: EPPLER 856 AIRFOIL (e856-il) Reynolds number: 1,000,000 Max Cl/Cd: 118.54 at α=8° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-e856-il-1000000-n5.txt Download as CSV file: xf-e856-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: EPPLER 856 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-18.000 -0.6936 0.11951 0.11683 -0.0505 1.0000 0.0040
-17.750 -0.7187 0.11116 0.10838 -0.0544 1.0000 0.0040
-17.500 -0.7477 0.10233 0.09943 -0.0586 1.0000 0.0040
-17.250 -0.7722 0.09453 0.09152 -0.0623 1.0000 0.0040
-17.000 -0.7991 0.08657 0.08343 -0.0662 1.0000 0.0040
-16.750 -0.8219 0.07958 0.07631 -0.0695 1.0000 0.0040
-16.500 -0.8446 0.07290 0.06951 -0.0726 1.0000 0.0039
-16.250 -0.8534 0.06702 0.06352 -0.0771 0.9994 0.0039
-16.000 -0.8551 0.06203 0.05842 -0.0814 0.9985 0.0040
-15.750 -0.8533 0.05758 0.05388 -0.0856 0.9973 0.0040
-15.500 -0.8531 0.05323 0.04942 -0.0896 0.9961 0.0041
-15.250 -0.8537 0.04893 0.04501 -0.0936 0.9949 0.0040
-15.000 -0.8481 0.04521 0.04119 -0.0978 0.9938 0.0040
-14.750 -0.8403 0.04254 0.03844 -0.1000 0.9922 0.0041
-14.500 -0.8355 0.03940 0.03522 -0.1027 0.9900 0.0041
-14.250 -0.8264 0.03646 0.03220 -0.1058 0.9877 0.0041
-14.000 -0.8134 0.03370 0.02936 -0.1094 0.9857 0.0042
-13.750 -0.8002 0.03082 0.02638 -0.1133 0.9841 0.0043
-13.500 -0.7934 0.02869 0.02418 -0.1143 0.9811 0.0044
-13.250 -0.7859 0.02675 0.02217 -0.1150 0.9764 0.0043
-13.000 -0.7696 0.02467 0.02002 -0.1177 0.9730 0.0045
-12.500 -0.7862 0.02145 0.01667 -0.1126 0.9424 0.0047
-12.250 -0.7635 0.02016 0.01530 -0.1143 0.9299 0.0048
-12.000 -0.7183 0.01885 0.01390 -0.1197 0.9205 0.0049
-11.750 -0.6529 0.01763 0.01257 -0.1290 0.9084 0.0051
-11.500 -0.5719 0.01652 0.01131 -0.1414 0.8876 0.0055
-11.250 -0.5390 0.01601 0.01055 -0.1437 0.8448 0.0056
-11.000 -0.5265 0.01571 0.01006 -0.1416 0.8101 0.0058
-10.750 -0.5132 0.01538 0.00959 -0.1395 0.7861 0.0059
-10.500 -0.4993 0.01498 0.00908 -0.1375 0.7659 0.0062
-10.250 -0.4831 0.01462 0.00862 -0.1359 0.7488 0.0065
-10.000 -0.4652 0.01429 0.00820 -0.1345 0.7331 0.0069
-9.750 -0.4464 0.01399 0.00781 -0.1332 0.7174 0.0072
-9.500 -0.4265 0.01371 0.00744 -0.1320 0.7030 0.0076
-9.250 -0.4057 0.01344 0.00708 -0.1310 0.6889 0.0081
-9.000 -0.3846 0.01312 0.00671 -0.1301 0.6771 0.0089
-8.750 -0.3625 0.01287 0.00638 -0.1292 0.6663 0.0096
-8.500 -0.3399 0.01260 0.00606 -0.1285 0.6556 0.0107
-8.250 -0.3169 0.01235 0.00576 -0.1278 0.6459 0.0120
-7.750 -0.2701 0.01186 0.00518 -0.1266 0.6256 0.0161
-7.500 -0.2464 0.01163 0.00492 -0.1260 0.6161 0.0194
-7.250 -0.2219 0.01141 0.00467 -0.1255 0.6070 0.0231
-7.000 -0.1974 0.01121 0.00444 -0.1250 0.5991 0.0271
-6.750 -0.1721 0.01101 0.00422 -0.1247 0.5913 0.0312
-6.500 -0.1473 0.01083 0.00400 -0.1242 0.5835 0.0363
-6.000 -0.0969 0.01043 0.00360 -0.1235 0.5679 0.0514
-5.750 -0.0712 0.01023 0.00341 -0.1232 0.5607 0.0620
-5.500 -0.0457 0.01003 0.00323 -0.1229 0.5537 0.0752
-5.250 -0.0199 0.00985 0.00307 -0.1226 0.5478 0.0899
-5.000 0.0060 0.00962 0.00290 -0.1224 0.5417 0.1088
-4.750 0.0316 0.00944 0.00274 -0.1222 0.5352 0.1301
-4.500 0.0577 0.00923 0.00259 -0.1220 0.5296 0.1537
-4.250 0.0837 0.00901 0.00245 -0.1218 0.5232 0.1829
-4.000 0.1093 0.00879 0.00230 -0.1215 0.5173 0.2192
-3.750 0.1353 0.00851 0.00216 -0.1214 0.5129 0.2646
-3.500 0.1617 0.00831 0.00207 -0.1212 0.5080 0.3076
-3.250 0.1883 0.00820 0.00203 -0.1211 0.5030 0.3381
-3.000 0.2154 0.00817 0.00200 -0.1209 0.4982 0.3553
-2.750 0.2429 0.00814 0.00198 -0.1209 0.4937 0.3689
-2.500 0.2702 0.00814 0.00196 -0.1208 0.4887 0.3790
-2.250 0.2972 0.00817 0.00196 -0.1206 0.4842 0.3885
-2.000 0.3248 0.00816 0.00195 -0.1205 0.4807 0.3976
-1.750 0.3524 0.00818 0.00196 -0.1205 0.4771 0.4071
-1.500 0.3796 0.00819 0.00198 -0.1204 0.4730 0.4190
-1.250 0.4066 0.00823 0.00199 -0.1202 0.4689 0.4272
-1.000 0.4337 0.00826 0.00201 -0.1201 0.4652 0.4327
-0.750 0.4613 0.00829 0.00202 -0.1200 0.4620 0.4369
-0.500 0.4886 0.00833 0.00204 -0.1199 0.4587 0.4405
-0.250 0.5156 0.00837 0.00206 -0.1197 0.4554 0.4442
0.000 0.5423 0.00842 0.00209 -0.1195 0.4519 0.4479
0.250 0.5692 0.00846 0.00213 -0.1193 0.4488 0.4519
0.500 0.5964 0.00850 0.00216 -0.1192 0.4459 0.4557
0.750 0.6234 0.00855 0.00220 -0.1190 0.4428 0.4587
1.000 0.6499 0.00859 0.00224 -0.1188 0.4398 0.4624
1.250 0.6759 0.00865 0.00229 -0.1184 0.4369 0.4663
1.500 0.7014 0.00872 0.00235 -0.1180 0.4339 0.4706
1.750 0.7278 0.00876 0.00240 -0.1177 0.4317 0.4743
2.000 0.7540 0.00881 0.00245 -0.1174 0.4290 0.4775
2.250 0.7799 0.00885 0.00251 -0.1171 0.4261 0.4817
2.500 0.8054 0.00891 0.00258 -0.1167 0.4233 0.4864
2.750 0.8306 0.00899 0.00265 -0.1162 0.4206 0.4908
3.250 0.8814 0.00913 0.00282 -0.1153 0.4158 0.4989
3.500 0.9071 0.00919 0.00290 -0.1150 0.4133 0.5041
3.750 0.9325 0.00926 0.00299 -0.1146 0.4107 0.5092
4.000 0.9575 0.00934 0.00309 -0.1141 0.4081 0.5140
4.250 0.9823 0.00944 0.00321 -0.1136 0.4056 0.5195
4.500 1.0065 0.00955 0.00333 -0.1129 0.4029 0.5250
4.750 1.0312 0.00965 0.00346 -0.1124 0.4005 0.5309
5.000 1.0566 0.00972 0.00357 -0.1120 0.3982 0.5380
5.250 1.0816 0.00981 0.00370 -0.1116 0.3957 0.5447
5.500 1.1063 0.00990 0.00383 -0.1111 0.3932 0.5512
5.750 1.1304 0.01002 0.00398 -0.1105 0.3904 0.5588
6.000 1.1538 0.01015 0.00413 -0.1098 0.3874 0.5667
6.250 1.1771 0.01028 0.00430 -0.1091 0.3846 0.5763
6.500 1.2015 0.01036 0.00445 -0.1086 0.3819 0.5857
6.750 1.2251 0.01048 0.00461 -0.1079 0.3779 0.5959
7.000 1.2473 0.01063 0.00479 -0.1070 0.3728 0.6063
7.500 1.2924 0.01091 0.00516 -0.1054 0.3624 0.6325
7.750 1.3131 0.01111 0.00538 -0.1042 0.3557 0.6479
8.000 1.3348 0.01126 0.00559 -0.1033 0.3501 0.6652
8.250 1.3553 0.01145 0.00583 -0.1021 0.3433 0.6840
8.500 1.3745 0.01166 0.00610 -0.1008 0.3374 0.7055
8.750 1.3951 0.01182 0.00635 -0.0997 0.3311 0.7336
9.000 1.4123 0.01207 0.00667 -0.0980 0.3235 0.7721
9.250 1.4294 0.01216 0.00697 -0.0962 0.3174 0.8405
9.500 1.4498 0.01233 0.00733 -0.0953 0.3076 1.0000
9.750 1.4678 0.01266 0.00766 -0.0938 0.2984 1.0000
10.000 1.4819 0.01314 0.00811 -0.0918 0.2862 1.0000
10.250 1.4948 0.01368 0.00860 -0.0896 0.2739 1.0000
10.500 1.5032 0.01440 0.00925 -0.0868 0.2559 1.0000
10.750 1.5074 0.01533 0.01007 -0.0835 0.2355 1.0000
11.000 1.5083 0.01643 0.01108 -0.0799 0.2145 1.0000
11.250 1.5100 0.01757 0.01213 -0.0766 0.1967 1.0000
11.500 1.5127 0.01872 0.01324 -0.0737 0.1827 1.0000
11.750 1.5131 0.02006 0.01453 -0.0706 0.1680 1.0000
12.000 1.5134 0.02151 0.01594 -0.0678 0.1552 1.0000
12.250 1.5136 0.02306 0.01747 -0.0653 0.1441 1.0000
12.500 1.5120 0.02485 0.01923 -0.0628 0.1326 1.0000
12.750 1.5091 0.02685 0.02120 -0.0605 0.1211 1.0000
13.000 1.5082 0.02884 0.02319 -0.0586 0.1119 1.0000
13.250 1.5078 0.03090 0.02526 -0.0570 0.1052 1.0000
13.500 1.5052 0.03324 0.02761 -0.0555 0.0973 1.0000
13.750 1.5013 0.03581 0.03018 -0.0541 0.0893 1.0000
14.250 1.4948 0.04115 0.03556 -0.0520 0.0772 1.0000
14.500 1.4893 0.04418 0.03861 -0.0511 0.0717 1.0000
14.750 1.4885 0.04685 0.04133 -0.0505 0.0678 1.0000
15.000 1.4805 0.05031 0.04480 -0.0499 0.0618 1.0000
15.250 1.4808 0.05300 0.04754 -0.0496 0.0593 1.0000
15.500 1.4739 0.05652 0.05109 -0.0493 0.0543 1.0000
15.750 1.4708 0.05971 0.05431 -0.0492 0.0505 1.0000
16.000 1.4655 0.06322 0.05785 -0.0492 0.0466 1.0000
16.250 1.4635 0.06640 0.06107 -0.0493 0.0439 1.0000
16.500 1.4577 0.07010 0.06480 -0.0495 0.0399 1.0000
16.750 1.4540 0.07363 0.06837 -0.0498 0.0368 1.0000
17.000 1.4509 0.07712 0.07189 -0.0502 0.0337 1.0000
17.250 1.4477 0.08067 0.07548 -0.0507 0.0313 1.0000
17.500 1.4448 0.08425 0.07910 -0.0513 0.0288 1.0000
17.750 1.4432 0.08769 0.08258 -0.0519 0.0268 1.0000
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